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A method for the calculation of external lift, moment, and pressure drag of slender open-nose bodies of revolution at supersonic speedsAn approximate method is presented for the calculation of the external lift, moment, and pressure drag of slender open-nose bodies of revolution of supersonic speeds. The lift, moment, and pressure drag of a typical ram-jet body shape are calculated at Mach numbers 1.45, 1.60, 1.75, and 3.00; and the lift and moment results are compared with available experimental data. The agreement of the calculated lift and moment data with the experimental data is excellent. The pressure-drag comparison was not presented because of the uncertainty of the amount of skin-friction drag present in the experimental results.
Document ID
19930091887
Acquisition Source
Legacy CDMS
Document Type
Other
Authors
Brown, Clinton E
Parker, Hermon M
Date Acquired
September 6, 2013
Publication Date
January 1, 1945
Report/Patent Number
NACA-TR-808
Accession Number
93R21177
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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